Rolf B Hansen81620 Avenue 49, Indio, CA 92201

5493293, Feb 20, 1996

Dec 2, 1991

7/803659

Rolf Hansen - Bellevue WA
Susan C. Kim - Bothell WA
Douglas S. Ormiston - Maple Valley WA

The Boeing Company - Seattle WA

G08B 2300

340968

A wind shear detection and alert system, compensated for the calibrated airspeed of the aircraft to minimize nuisance wind shear alerts. The wind shear detection and alert system (10) determines a reference airspeed as a function of flap position, with respect to a minimum maneuver airspeed signal (60) provided by a stall warning computer on the aircraft. The reference airspeed is subtracted from a calibrated airspeed signal (76) that has been filtered to remove minor variations in the signal using a Laplace filter (68). The differential airspeed is further filtered by another Laplace filter (78), producing a filtered differential airspeed signal (70), which the system uses to determine a delta threshold (48) to be applied in compensation for the aircraft airspeed to a wind shear alert reference signal. As the filtered differential airspeed increases, the delta threshold signal increases the absolute level of the wind shear alert threshold, reducing the likelihood of unnecessary wind shear alerts.

4354237, Oct 12, 1982

Jun 24, 1980

6/162451

Antonius A. Lambregts - Renton WA
Rolf Hansen - Bellevue WA

The Boeing Company - Seattle WA

G06G 778
G05D 112

364428

Aircraft altitude, ground velocity, and altitude rate signals are input to a computer which, using a unique control law, generates a pitch control surface command signal suitable for guiding an aircraft on its flare path to a specified runway touchdown point despite varying wind conditions.

4419732, Dec 6, 1983

Sep 14, 1981

6/301911

Antonius A. Lambregts - Issaquah WA
Rolf Hansen - Bellevue WA

The Boeing Company - Seattle WA

G06G 778
G05D 112

364428

An improved inner loop control is disclosed for use in an aircraft pitch axis control system. Signals representative of vertical acceleration and pitch rate are complementary filtered and summed to produce an "inner loop" damping signal which is combined with "outer loop" command signals to produce an elevator control signal. The improved approach provides higher outer loop control law gains and better system stability, resulting in higher control bandwidth and tighter command tracking, especially in turbulence.

4357661, Nov 2, 1982

Feb 22, 1980

6/123529

Antonius A. Lambregts - Renton WA
Rolf Hansen - Bellevue WA

The Boeing Company - Seattle WA

G05D 112
G06G 770
B64C 1318

364430

Upon aircraft landing approach, flare path command signals of altitude, vertical velocity and vertical acceleration are generated as functions of aircraft position and velocity with respect to the ground. The command signals are compared with corresponding actual values to generate error signals which are used to control the flight path.